Control means for aircraft



April 16, 1946. A, M KJNG I 2,398,710

CONTROL MEANS FOR AIRCRAFT Filed Oct. 6, 1944 5 Sheets-Sheet 1 '7 Inventor 4 Z April 16, 1946. A. M KING 2,398,710

CONTROL MEANS FOR AIRCRAFT Filed 001;. 6, 1944 s Sheets-Sheet 2 In rumor April 16, 1946. A. M. KING I CONTROL MEANS FOR AIRCRAFT Filed ot. 6, 1944 5 Sheets-Sheet 5 I nuentor Patented Apr. 16, 1946 "UNITED STATES PATENT OFFICE coN'rRoL MEANS FOR AIRCRAFT Arthur M, King, Phoenix, Ariz. Application October 6, 1944;, Serial No. 557,463

3 Claims. (01.244wl13) his vent on ela es o ntrol me r aircraft, and more particularly to improved separable on l, surface or airqraft a pt to fi ct a r u tion p ed the airc ait. Se ing s a rake.

A mary b ect f in ention s the P vision f a im ov rudd r h v n scram e t ons s cia d the wit whereb to r e h dr f a lane assage thr gh the r and corres on ing y reduce ts e d- A further important obiect, is th provision of such a rudder which will, at reduced speed of the plane, act to effect an increased turn of the plane, with a reduced movement of the rudder control.

Still another object of this invention is the provision of improved means for effecting the separation of the separable portions of'the rudder, controllable from a. remote point in the plane.

A u r and more spe ifi ob ct s e on vision of r ed l cking means. fo hold n the separable portions of the rudder in assemble relation, in the use Of the device when the brake isnot desired.

Still another ObJ'Qct is, the provision of improved meansfor effecting the separation or separable portions of any Control Surface of an airplane, such as the elevators, or th ailerons, or diving flaps or the like.

Still another object resides in the prcvision of a device of this character which will be sturdy and durableinconstruction, reliable and efiicient in operation, and relatively simple and inexpene sive to manufacture and install, for'applicatien to conventional airplanes. I

Still other objects reside in the combinations of elements, arrangements of parts, and features of construction, all as will be more fully pointed out hereinafter and disclosed in the accompanying drawings, wherein there are shown preferred embodiments of this inventive concept.

Having reference now to the drawings:

Fi ure 1 i a t prlan View of a ragment of e t i s mb y f anair lana r ided with one form of device embodying features of this invention, shown in open position, certain concealed portions of the mechanism being shown in dotted lines.

Figure 2 is an enlarged fragmentary top plan view of portions of the mechanism shown in Figure 1.

Figure 3 is a sectional view taken substantially along the line 3-53 of Figure 2, as viewed in the direction indicated by the arrows.

Figure 4 is an enlarged side elevational view of certain portions of the operating mechanism.

Figure 5 is a top plan View showing a fragment of the mechanism disclosed in Figures 2 and 4, in a different position of adjustment.

Figure 6 is a view similar to Figure 4, showing a modified form of construction, and

Figure 7 is a fragmentary perspective view showing portions of the operating mechanism disclosed in Figure 6.

Like. reference numerals refer to like parts throughout the several views of the drawings.

Having reference now to the drawings, "and more particularly to Figure 1, there is generally indicated at H! a portion of the tail assembly of an airplane, comprised of horizontal stabilizers H, elevators I2 provided with trim tabs 13, a vertical stabilizer l4, and a rudder generally indicated at l5. Rudder I5 is comprised of a supportin frame It and two separable outer members l1, so arranged that when the members I! are closed adjacent the members [6, the rudder assembly forms a streamlined unit aligned behind the vertical stabilizer I4, adapted to be controlled in any desired manner by conventional controls extending from control members in the'pilots cockpit.

The separable members .17 are mounted, as on plates i8, adapted for rotation, or pivotal movement, about a rudder post I 9. Secured to the inner side of each of members I! is a lug to which is secured in pivotal relation, as by a pivot pin 2!, one end of a bell crank member 22, the oppesite end of which is mounted on and secured to a squared end of a bolt or pin 23, being held in position, as by a nut 24, bolt 23 being secured within suitable bores or sleeves in a block generally indicated at 25. s As best shown in Figure 4, the opposite ends of bolt 23. extend completely through the block 25, and have secured to their extremities, as by means of nuts 24a, bell crank members 22a similar to and aligned with members 22, and secured to corresponding lugs below and aligned with lugs 29 on separable members l'l,

Block is provided with a threaded bore 25 extending horizontally therethrough (see Fig.3), Within which is positioned for rotation a threaded shaft or red 21. One end of rod 21 is journaled in the outer extremity of rudder frame I 6, and the other end passes into the interior of the plane fuselage, wherein is positioned any desired source f power, such as an electric motor (not shown) adapted to rotate the rod when suitably energized.

From the foregoing it will now be seen that when it is desired to separate the separable portions I! of the rudder, inorder to effect a braking action on the speed of the plane, it is merely necessary to rotate the rod 21, which rotation causes movement of the block 25 and its associated bell crank members 22 from the position hown n Fi u e 5 to th Pos t on o n n ure 2, or any intermediate point therebetween, thus effecting a separation of the members IT,

which serve to increase the drag of the plane, creating a partial vacuum between the extremities thereof and accordingly slowing down the plane. 7

Means are also provided for locking theseparable portions in closed position when it is desired to use the rudder in a conventional manner. Such means take the form of projections 35 extending from the interior surfaces of members l1, and provided with apertures 3|, which apertures are adapted to be engaged by a pin 32 provided with a wedge-shaped point 33 secured to block 25. As the block 25 is drawn forwardly toward the fuselage of the plane, the wedgeshaped point 33 disengages the apertures 3| simultaneously with the concurrent separation of members I! effected by bell crank levers 22. Conversely, as the members I! are closed toward the frame I5, the members 30 are brought inwardly until the apertures 3| are in registering alignment adjacent point 33 of the pin 32, which, as the block 25 moves forwardly, is adapted to engage the same and securely hold the parts in closed position.

From the foregoing it will now be seen that with the members I! in spread or partially spread position, a maximum control over the direction of flight of the aircraft may be achieved with a minimum movement of the rudder, due to the fact that either of members II has a distance to travel, in order to achieve full right or left rudder position, of approximately half that of the path of travel of the normal rudder, and that when such movement of one of the members either'to the right or left is achieved, the other of members I! is positioned out of the slip stream behind the vertical stabilizer, in such manner that the entire ruddering effect is accomplished by the other of the members l1. Thus, it will be seen that a maximum flexibility of controls assure to the aircraft a low speed with a minimum movement of the rudder controls.

Various means may be employed for effecting the separation of separable members H, as. well as various means for locking the portions in assembled inoperative position. An alternative form of means for moving the separable portions is disclosed in Figure 6, and takes the form of a block 55 having a bore therethrough, which, however, is smooth instead of threaded, as is bore 26, through which is adapted to be passed a smooth rod or shaft 51. Vertical bores accommodate pins 53 provided with nuts 54 adapted to secure bell crank levers 52 substantially identical to bell crank levers 22. Similarly, the opposite ends of pins 23 are provided with nuts 54a adapted to hold in position bell crank levers 52a similar to the levers 22a. A relatively heavy compression spring 50 surrounds rod 51 on the interiorside thereof, and abuts block 55, and the movement of the block 55 is effected by a control cord or cable 6| secured to an eye 62 on the inner side of the block, a pull on the cable effecting movement of the block in a direction 'to separate the separable members l1, and the resiliency of the spring 60 serving to force the block,.and correspondingly the members IT, back into closed position when the force on cable BI is released.

An alternative form of lock construction is also shown in Figures 6 and 7, and takes the form of an upwardly extending lug 65 having a transverse slot therethrough, secured to the pp P tion of block 55, in which slot is positioned a twisted sheet metal plate 66. Plate 66 has secured thereto a plate 61 provided with a pin 68 adapted to engage in an arcuate slot 69 in a cam member 15. The opposite end of twisted member 65 extends through a slot in a plat H associated with member 19, whereby linear movement f the block 55 and lug E5 is transmitted to rotary movement of plate 61 and hence pin 58 which, through its engagement with slots 69 moves cam member 15. The cam member I0 is provided with two depressions 12, adapted to engage transversely extending pins I3 carried by lug 14 similar in position to members 30 in the foregoing modification. Thus, it will be seen that as the block 55 is moved toward the tail of the plane in such manner as to close the separable portions H, the cam member 10 is rotated until depressions or grooves l2 engage pins 13. whereupon the separable members H are held securely against separation.

Obviously, various other modes of operation for the movement of the block adapted to separate the separable members may be utilized if desired, as, for example, hydraulic means effecting movement of the block through a rack and pinion, or other known mechanical movements.

Equally obviously, while the device has been herein described as associated with the rudder of a plane, it will be understood that the mechanism for separating the separable parts of the device may be equally well associated with diving flaps, elevators, or other control surfaces of the plane.

Now, from the foregoing it will be seen that there is herein provided a mechanism accomplishing all the objects of this invention and others, including many advantages of great practical utility and commercial importance.

As many embodiments may' be made of this inventive concept, and as many modifications may be made in the embodiments hereinbefore shown and described, it is to be understood that all matter herein is to be interpreted merely as illustrative and not in a limiting sense.

I claim:

1. In a rudder for aircraft, in combination, a

frame, two separable rudder surfaces pivotally secured to said frame, and means for separating and closing said surfaces, aid means including a movable block, link members pivotally secured to said block and said surfaces, a threaded rod engageable in a threaded bore rotatable to move said block, and means including a pin carried by said block for locking said surfaces in closed position. 2. In a rudder for aircraft, in combination, a frame, two separable rudder surfaces pivotally secured to said frame, means for separating and closing said surfaces, and means for locking said surfaces in closed position, said means including a'movable block, lugs having apertures therein associated with said surfaces, and a pin on said block engageable in said apertures.

3. In a control surface for aircraft, a frame, two separable control surfaces pivotally secured to said frame, means for separating and closing said surfaces, said means including a movable block, link members pivotally secured to aid block and said surfaces, means for moving said block, and means for locking said surfaces in closed position, said means including lugs having apertures therein associated with said surfaces, and a pin on said block engageable in said apertures.

' ARTHUR M. KING. 

